Diamond DA42 Twin Star Aircraft Flight Manual

Introduction DA 42 AFM

Page 0 - 0a Rev. 5 15-Nov-2007 Doc. # 7.01.05-E

NOTE'This airplane flight manual is valid for DA42 airplanes with'a KAP 140 or no autopilot system installed.'

Refer to the airplane flight manual DA42 with Garmin'GFC 700 (OM 42-102), Doc. No. 7.01.06-E for airplanes'with a Garmin Autopilot system installed.'

DA 42 AFM Introduction

Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 0 - 1

FOREWORD

We congratulate you on the acquisition of your new DIAMOND DA 42 Twin Star.

Skillful operation of an airplane increases both safety and the enjoyment of flying.Please take the time therefore, to familiarize yourself with your new DIAMOND DA 42.

This airplane may only be operated in accordance with the procedures and operatinglimitations of this Airplane Flight Manual.

Before this airplane is operated for the first time, the pilot must familiarize himself withthe complete contents of this Airplane Flight Manual.

In the event that you have obtained your DIAMOND DA 42 second-hand, please let usknow your address, so that we can supply you with the publications necessary for thesafe operation of your airplane.

This document is protected by copyright. All associated rights, in particular those oftranslation, reprinting, radio transmission, reproduction by photo-mechanical or similarmeans and storing in data processing facilities, in whole or part, are reserved.

Copyright by: DIAMOND AIRCRAFT INDUSTRIES GMBHN.A. Otto-Strasse 5A-2700 Wiener Neustadt, AustriaPhone : +43-2622-26700Fax : +43-2622-26780E-Mail : [email protected]


Page 0 - 2 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E

0.1 APPROVAL

The content of approved chapters is approved by EASA. All other content is approvedby DAI under the authority of EASA DOA No. EASA.21J.052 in accordance withPart 21.

0.2 RECORD OF REVISIONS

All revisions of this manual, with the exception of - Temporary Revisions, updates of the modification level (Section 1.1), updated mass and balance information (Section 6.3), updates of the Equipment Inventory (Section 6.5), and updates of the List of Supplements (Section 9.2) must be recorded in the following table.

The new or amended text is indicated by a vertical black line at the left hand side of therevised page, with the revision number and date appearing at the bottom of the page.

If pages are revised which contain information valid for your particular serial number(modification level of the airplane, weighing data, Equipment Inventory, List ofSupplements), then this information must be transferred to the new pages in hand-writing.

The cover pages of Temporary Revisions, if applicable, are inserted behind the coverpage of this manual; the following pages of the Temporary Revision are inserted in frontof the corresponding pages of this AFM. Temporary Revisions are used to provideinformation on systems or equipment until the next 'permanent' Revision of the AirplaneFlight Manual. When a 'permanent' Revision covers a Mandatory or Optional DesignChange Advisory (MM or OM), then the corresponding Temporary Revision issuperseded. Example: Revision 3 covers OM 42-053, therefore the TemporaryRevision TR-OM-42-053 is superseded by the 'permanent' Revision 3.



Rev.No. Reason

Chap-ter Page(s)

Date ofRevision Approval Verification

DateInserted Signature

1IFR

certification;

correctionsall all exceptcover page 1 Dec 2004 2005-196

[Ing. AndreasWinkler for

ACG]

2

MM 42-034(elevator

stop);

OM 42-060(T&B

coordinat.);

Take-offdiagrams

0

4A

4B

5

6

7

0-3, 0-5,

0-7, 0-8, 0-9

4A-9

4B-25

5-11, 5-12

6-18

7-7

28 Jan 2005

[10 Feb 2005

Dipl.-Ing.(FH)

ManfredReichel

for DAI]

3

FAA

Certification

MM 42-

-062, -070/a,

-079, -080,

-091, -101,

-111/b

(TR-MM-42-111/a),

-115

OM 42-

-053, -056,

-057, -059,

-079

Corrections

all all 15 Oct 2005

[25 Oct 2005

Ing. AndreasWinkler for

ACG]


Rev.No. Reason

Chap-ter Page(s)

Date ofRevision Approval Verification

DateInserted Signature


4

MM 42-

-037, -046,

-063, -088,

OM 42-

-054, -077,

-080

corrections

0 0-3 thru 0-10

30 Nov2005

EASAA.C.

2618

[20 Dec 2005'Ing. Andreas'Winkler for'

ACG]'

1 1-2, 1-11

2

2-2, 2-4, 2-7,

2-8, 2-10, 2-14,

2-15, 2-18,

2-21 thru 2-23,

2-26, 2-27, 2-32

33-30, 3-31,

3-32, 3-38

4A all (4A-1 thru4A-40)

4B

4B-2, 4B-13,

4B-25, 4B-27,

4B-30 thru

4B-34

5 all (5-1 thru5-34)

6

6-5, 6-8,

6-10 thru 6-14,

6-16, 6-20

77-1, 7-2,

7-40 thru 7-66

8 8-4, 8-12

9 9-2



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DA 42 AFM General


CHAPTER 1GENERAL

Page

1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-41.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . 1-41.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-51.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . 1-71.6 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-15

1.6.1 CONVERSION FACTORS . . . . . . . . . . . . . . . . . . . . . . . . . . 1-151.6.2 CONVERSION CHART LITERS / US GALLONS . . . . . . . . . 1-17

1.7 THREE-VIEW DRAWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-181.8 G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-191.9 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21

1.9.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-211.9.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-221.9.3 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-22

General DA 42 AFM


1.1 INTRODUCTION

This Airplane Flight Manual has been prepared in order to provide pilots and instructorswith all the information required for the safe and efficient operation of the airplane.

The Airplane Flight Manual includes all the data which must be made available to the pilotaccording to the JAR-23 requirement. Beyond this, it contains further data and operatinginstructions which, in the manufacturers opinion, could be of value to the pilot.

This Airplane Flight Manual is valid for all serial numbers with a KAP 140 or no autopilot'system installed. Equipment and modification level (design details) of the airplane may'vary from serial number to serial number. Therefore, some of the information containedin this manual is applicable depending on the respective equipment and modification level.The exact equipment of your serial number is recorded in the Equipment Inventory inSection 6.5. The modification level is recorded in the following table (as far as necessaryfor this manual).

Modification Source Installed

Use of Diesel Fuel MM 42-037 9 yes 9 no

Increased Take-Off Mass MM 42-088 9 yes 9 noNew Engine Instrument Markings MM 42-101 9 yes 9 no

Autopilot Static Source' MM 42-186' 9 yes' 9 no'

TAE 125-02-99 Engine' MM 42-198' 9 yes' 9 no'ECU Backup Battery' MM 42-240' 9 yes' 9 no'

Ice Protection System OM 42-053 9 yes 9 no

Ice Protection System

(Known Icing)OM 42-054 9 yes 9 no

DA 42 AFM General

Modification Source Installed


Oxygen System' OM 42-055' 9 yes' 9 no'

Auxilary Fuel Tanks' OM 42-056' 9 yes' 9 no'Front Seats with Adjustable'Backrest' OM 42-067' 9 yes' 9 no'

Electrical Rudder Pedal'Adjustment' OM 42-070' 9 yes' 9 no'

Mission Power Supply System' OM 42-074' 9 yes' 9 no'Removable Fuselage Nose Cone OM 42-077 9 yes 9 no

ECU Backup Battery' OM 42-129' 9 yes' 9 no'

This Airplane Flight Manual must be kept on board the airplane at all times. Its designatedplace is the side bag of the forward left seat. The designated place for the Garmin G1000Cockpit Reference Guide is the bag on the rear side of the forward left seat.

CAUTIONThe DA 42 is a twin engine airplane. When the operatinglimitations and maintenance requirements are complied with,it has the high degree of reliability which is required by thecertification basis. Nevertheless, an engine failure is notcompletely impossible. For this reason it is highly recom-mended for flights during the night, on top, under IMC, orabove terrain which is unsuitable for a landing, to select flighttimes and flight routes such that reduced performance in caseof single engine operation does not constitute a risk.

General DA 42 AFM


1.2 CERTIFICATION BASIS

The certification basis is JAR-23, published on 11-Mar-1994, including Amdt. 1, andadditional requirements as laid down in CRI A-01.

1.3 WARNINGS, CAUTIONS AND NOTES

Special statements in the Airplane Flight Manual concerning the safety or operation ofthe airplane are highlighted by being prefixed by one of the following terms:

WARNINGmeans that the non-observation of the correspondingprocedure leads to an immediate or important degradationin flight safety.

CAUTIONmeans that the non-observation of the correspondingprocedure leads to a minor or to a more or less long termdegradation in flight safety.

NOTEdraws the attention to any special item not directly related tosafety but which is important or unusual.

DA 42 AFM General


1.4 DIMENSIONS

NOTEAll dimensions shown below are approximate.

Overall dimensions

Span : 13.42 m 44 ft

'' 13.55 m' 44.5 ft including ACL'

Length : 8.56 m 28 ft 1 in

Height : 2.49 m 8 ft 2 in

Wing

Airfoil : Wortmann FX 63-137/20 - W4

Wing Area : 16.29 m 175.3 sq.ft.

Mean aerodynamic chord : 1.271 m 4 ft 2 in

Aspect ratio : 11.06

Dihedral : 5

Leading edge sweep : 1

Aileron

Area (total, left + right) : 0.66 m 7.1 sq.ft.

General DA 42 AFM


Wing flaps

Area (total, left + right) : 2.18 m 23.4 sq.ft.

Horizontal tail

Area : 2.35 m2 25.3 sq.ft.

Elevator area : 0.66 m 7.1 sq.ft.

Angle of incidence : -1.1 relative to longitudinal axis of airplane

Vertical tail

Area : 2.43 m 26.2 sq.ft.

Rudder area : 0.78 m 8.4 sq.ft.

Landing gear

Track : 2.95 m 9 ft 8 in

Wheelbase : 1.735 m 5 ft 8 in

Nose wheel : 5.00-5; 10 PR, 120 mph

Main wheel : 15x6.0-6; 6 PR, 120 mph

DA 42 AFM General


1.5 DEFINITIONS AND ABBREVIATIONS

(a) Airspeeds

CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrumenterrors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL.

IAS: Indicated Airspeed as shown on an airspeed indicator.

KCAS: CAS in knots.'

KIAS: IAS in knots.'

TAS: True Airspeed. The speed of the airplane relative to the air. TAS is CAScorrected for errors due to altitude and temperature.

vA: Maneuvering Speed. Full or abrupt control surface movement is not permissibleabove this speed.

vFE: Maximum Flaps Extended Speed. This speed must not be exceeded with thegiven flap setting.

vLO: Maximum Landing Gear Operating Speed. This speed may not be exceededduring the extension or retraction of the landing gear.

vLE: Maximum Landing Gear Extended Speed. This speed may not be exceededif the landing gear is extended.

vmCA: Minimum Control Speed. Minimum speed necessary to be able to control theairplane in case of one engine inoperative.

vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in anyoperation.

General DA 42 AFM


vNO: Maximum Structural Cruising Speed. This speed may be exceeded only insmooth air, and then only with caution.

vS: Stalling Speed, or the minimum continuous speed at which the airplane is stillcontrollable in the given configuration.

vS0: Stalling Speed, or the minimum continuous speed at which the airplane is stillcontrollable in the landing configuration.

vS1: Stalling Speed, or the minimum continuous speed at which the airplane is stillcontrollable with flaps and landing gear retracted.

vSSE: Minimum Control Speed for Schooling. Minimum speed necessary in case ofone engine intentionally inoperative / idle (training purposes).

vx: Best Angle-of-Climb Speed.

vy: Best Rate-of-Climb Speed.

vYSE: Best Rate of-Climb Speed for one engine inoperative.

(b) Meteorological terms

ISA: International Standard Atmosphere. Conditions at which air is identifiedas an ideal dry gas. The temperature at mean sea level is 15 C (59 F),air pressure at MSL is 1,013.25 hPa (29.92 inHg); the temperaturegradient up to the altitude at which the temperature reaches -56.5 C(-69.7 F) is -0.0065 C/m (-0.00357 F/ft), and above this 0 C/m (0 F/ft).

MSL: Mean Sea Level.

OAT: Outside Air Temperature.

DA 42 AFM General


QNH: Theoretical atmospheric pressure at MSL, calculated from the elevationof the measuring point above MSL and the actual atmospheric pressureat the measuring point.

Density Altitude:Altitude in ISA conditions at which the air density is equal to the currentair density.

Indicated Pressure Altitude:Altitude reading with altimeter set to 1,013.25 hPa (29.92 inHg).

Pressure Altitude:Altitude indicated by a barometric altimeter, which is set to 1,013.25 hPa(29.92 inHg). The Pressure Altitude is the Indicated Pressure Altitudecorrected for installation and instrument errors.

In this Airplane Flight Manual altimeter instrument errors are regardedas zero.

Wind: The wind speeds which are shown as variables in the diagrams in thismanual should be regarded as headwind or tailwind components of themeasured wind.

(c) Flight performance and flight planning

AGL: Above Ground Level.'

Demonstrated Crosswind Component:The speed of the crosswind component at which adequate maneuverabil-ity for take-off and landing has been demonstrated during typecertification.

General DA 42 AFM


MET: Weather, weather advice.

NAV: Navigation, route planning.

RoC: Rate of Climb.

(d) Mass and balance

CG: Center of Gravity, also called 'center of mass'. Imaginary point in whichthe airplane mass is assumed to be concentrated for mass and balancecalculations. Its distance from the Datum Plane is equal to the Centerof Gravity Moment Arm.

Center of Gravity Moment Arm:The Moment Arm which is obtained if one divides the sum of the individualmoments of the airplane by its total mass.

Center of Gravity Limits:The Center of Gravity range within which the airplane, at a given mass,must be operated.

DP: Datum Plane; an imaginary vertical plane from which all horizontaldistances for center of gravity calculations are measured.

Empty Mass: The mass of the airplane including unusable fuel, all operating fluids and'the maximum quantity of oil.

Maximum Take-off Mass:The maximum permissible mass for take-off.

Maximum Landing Mass:The highest mass for landing conditions at the maximum descent velocity.This velocity was used in the strength calculations to determine thelanding gear loads during a particularly hard landing.

DA 42 AFM General


Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravityof a component.

Moment: The mass of a component multiplied by its moment arm.

Usable Fuel: The quantity of fuel available for flight planning.

Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight.

Useful Load: The difference between take-off mass and empty mass.

(e) Engine

ECU: Engine Control Unit.

FADEC: Full Authority Digital Engine Control.

RPM: Revolutions per minute (rotational speed of the propeller).

Engine starting fuel temperature:Above this fuel temperature the engine may be started.

Take-off fuel temperature:Above this fuel temperature take-off power setting is permitted.

General DA 42 AFM


(f) Designation of the circuit breakers on the instrument panel

LH MAIN BUS:

COM1 COM Radio No. 1GPS/NAV1 Global Positioning System and NAV Receiver No. 1XPDR TransponderENG INST Engine InstrumentsPITOT Pitot Heating SystemXFR PUMP/DE-ICE Fuel Transfer Pump / De-Icing SystemTAXI/MAP/ACL Taxi-, Map-, Anti Collision LightFLOOD/OXY Flood Light / Oxygen SystemPFD Primary Flight DisplayADC Air Data ComputerAHRS Attitude Heading Reference SystemGEAR WRN/ELEV. LIMIT Landing Gear Annunciation / Variable Elevator StopGEAR Landing Gear Control

RH MAIN BUS:

MFD Multi Function DisplayAH Artificial HorizonSTALL WRN Stall Warning SystemFLAP Flap SystemLDG LT/START Landing Light / StartINST LT/ NAV LT Instrument-, Navigation (Position) LightAV/CDU/FAN Avionic-, CDU-Cooling FansAVIONIC BUS Avionic BusAV CONT. Avionic Control'

DA 42 AFM General


AVIONICS BUS:

COM2 COM Radio No. 2GPS/NAV2 Global Positioning System and NAV Receiver No. 2AUDIO Audio PanelAUTO PILOT Auto Pilot SystemWx 500 StormscopeADF Automatic Direction FinderDME Distance Measuring EquipmentWx RDR Weather RadarTAS Traffic Advisory System'DATA LINK GDL 69A Data Link System'

LH ENG ECU BUS:

ECU BUS LH ECU BusECU B LH ECU BECU A LH ECU A

LH BUS:

ALT.LH LH AlternatorBATT Battery

RH BUS:

ALT.RH RH AlternatorBATT Battery

General DA 42 AFM


RH ENG ECU BUS:

ECU BUS RH ECU BusECU B RH ECU BECU A RH ECU A

(g) Equipment

ELT: Emergency Locator Transmitter.

(h) Design Change Advisories

MM: Mandatory Design Change Advisory.OM: Optional Design Change Advisory.

(i) Miscellaneous

ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation).

ATC: Air Traffic Control.

CFRP: Carbon Fiber Reinforced Plastic.

EASA: European Aviation Safety Agency.

EPU: External Power Unit.

GIA: Garmin Integrated Avionics.

GFRP: Glass Fiber Reinforced Plastic.

JAR: Joint Aviation Requirements.

JC/VP: Joint Certification/Validation Procedure.

PCA: Primary Certification Authority.

DA 42 AFM General


1.6 UNITS OF MEASUREMENT

1.6.1 CONVERSION FACTORS

Dimension SI-Units US Units Conversion

Length [mm] millimeters

[m] meters

[km] kilometers

[in] inches

[ft] feet

[NM] nauticalmiles

[mm] / 25.4 = [in]

[m] / 0.3048 = [ft]

[km] / 1.852 = [NM]

Volume [l] liters [US gal] US gallons

[qts] US quarts

[l] / 3.7854 = [US gal]

[l] / 0.9464 = [qts]

Speed [km/h] kilometersper hour

[m/s] meters persecond

[kts] knots

[mph] miles perhour

[fpm] feet perminute

[km/h] / 1.852 = [kts]

[km/h] / 1.609 = [mph]

[m/s] x 196.85 = [fpm]

Speed ofrotation

[RPM] revolutions per minute --

Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb]

Force,weight

[N] newtons [lbf] poundsforce

[N] x 0.2248 = [lbf]

Pressure [hPa] hecto-pascals

[mbar] millibars

[bar] bars

[inHg] inches ofmercury

[psi] pounds persquare inch

[hPa] = [mbar]

[hPa] / 33.86 = [inHg]

[bar] x 14.504 = [psi]

Tempera-ture

[C] degreesCelsius

[F] degreesFahrenheit

[C]x1.8 + 32 = [F]

([F] - 32)/1.8 = [C]

General DA 42 AFM

Dimension SI-Units US Units Conversion


Intensity ofelectriccurrent

[A] ampres --

Electriccharge(batterycapacity)

[Ah] ampre-hours

--

Electricpotential

[V] volts --

Time [sec] seconds --

DA 42 AFM General


1.6.2 CONVERSION CHART LITERS / US GALLONS

Liters US Gallons US Gallons Liters

5 1.3 1 3.8

10 2.6 2 7.6

15 4.0 4 15.1

20 5.3 6 22.7

25 6.6 8 30.3

30 7.9 10 37.9

35 9.2 12 45.4

40 10.6 14 53.0

45 11.9 16 60.6

50 13.2 18 68.1

60 15.9 20 75.7

70 18.5 22 83.3

80 21.1 24 90.9

90 23.8 26 98.4

100 26.4 28 106.0

110 29.1 30 113.6

120 31.7 32 121.1

130 34.3 34 128.7

140 37.0 36 136.3

150 39.6 38 143.8

160 42.3 40 151.4

170 44.9 45 170.3

180 47.6 50 189.3

General DA 42 AFM


1.7 THREE-VIEW DRAWING

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

'

2950

mm

(9 ft

8 in

)

1870

mm

(6 ft 2

in)

1342

0 m

m (4

4 ft

0 in

)

1735

mm

8560

mm

(28

ft 1

in)

2490 mm

(8 ft 2 in)

1950 mm

(6 ft 5 in)

2205 mm

(7 ft 3 in)

(5 ft

8 in

)

1355

0 m

m (4

4.5

ft) in

clud

ing

AC

L

DA 42 AFM General


1.8 G1000 AVIONICS SYSTEM

1. The G1000 Integrated Avionics System is a fully integrated flight, engine,communication, navigation and surveillance instrumentation system. The systemconsists of a Primary Flight Display (PFD), Multi-Function Display (MFD), audio panel,Air Data Computer (ADC), Attitude and Heading Reference System (AHRS), enginesensors and processing unit (GEA), and integrated avionics (GIA) containing VHFcommunications, VHF navigation, and GPS (Global Positioning System).

2. The primary function of the PFD is to provide attitude, heading, air data, navigation,and alerting information to the pilot. The PFD may also be used for flight planning.The primary function of the MFD is to provide engine information, mapping, terraininformation, and for flight planning. The audio panel is used for selection of radios fortransmitting and listening, intercom functions, and marker beacon functions.

3. The primary function of the VHF Communication portion of the G1000 is to enableexternal radio communication. The primary function of the VOR/ILS Receiver portionof the equipment is to receive and demodulate VOR, Localizer, and Glide Slope signals.The primary function of the GPS portion of the system is to acquire signals from theGPS satellites, recover orbital data, make range and Doppler measurements, andprocess this information in real-time to obtain the user*s position, velocity, and time.

4. Provided a Garmin G1000 GPS receiver is receiving adequate usable signals, it hasbeen demonstrated capable of and has been shown to meet the accuracy specificationsfor:

(a) VFR/IFR enroute, oceanic, terminal, and non-precision instrument approach (GPS,Loran-C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation within theU.S. National Airspace System in accordance with AC 20-138A.

General DA 42 AFM


(b) RNAV (GPS) Approaches - The G1000 GPS meets the requirements ofAC 20-138(A) for GPS based RNAV approaches. This includes RNAV approacheslabeled as RNAV (GPS), provided GPS sensor data is valid.

(c) The system meets the accuracy of RNP5 airspace (BRNAV) requirements ofAC 90-96 and in accordance with AC 20-138A, EASA AMC 20-4, and FAA Order8110.60 for oceanic and remote airspace operations, provided it is receiving usablenavigation information from the GPS receiver.

Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference datum.GPS navigation data is based upon use of only the GPS operated by the United Statesof America.

DA 42 AFM General


1.9 SOURCE DOCUMENTATION

This section lists documents, manuals and other literature that were used as sources forthe Airplane Flight Manual, and indicates the respective publisher. However, only theinformation given in the Airplane Flight Manual is valid.

1.9.1 ENGINE

Address: Thielert Aircraft Engines GmbHPlatanenstrasse 14D-09350 LichtensteinGERMANY

Phone: +49-(37204)-696-90Fax: +49-(37204)-696-50Website: www.thielert.com

Documents: TAE 125-01 Operation and Maintenance Manual

or'

TAE 125-02-99 Operation and Maintenance Manual '(if MM 42-198 carried out)'

General DA 42 AFM


1.9.2 PROPELLER

Address: mt-propellerAirport Straubing WallmhleD-94348 AttingGERMANY

Phone: +49-(9429)-9409-0E-mail: [email protected]: www.mt-propeller.de

Documents: E-124, Operation and Installation ManualHydraulically controlled variable pitch propellerMTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25

1.9.3 AVIONICS SYSTEM

Address: Garmin International, Inc.1200 East 151st StreetOlathe, Kansas 66062USA

Phone: +1-(913)-3978200

Fax: +1-(913)-3978282

Website: www.garmin.com

Documents: G1000 Cockpit Reference GuideP/N 190-00406-00, Sept. 2004

DA 42 AFM Operating Limitations


CHAPTER 2OPERATING LIMITATIONS

Page

2.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-42.3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . 2-52.4 POWER-PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-62.5 ENGINE INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . 2-92.6 WARNING, CAUTION AND ADVISORY ALERTS . . . . . . . . . . . . . 2-11

2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11

2.6.2 OTHER WARNING ALERTS . . . . . . . . . . . . . . . . . . . . . . . . 2-142.7 MASS (WEIGHT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-152.8 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-162.9 APPROVED MANEUVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-172.10 MANEUVERING LOAD FACTORS . . . . . . . . . . . . . . . . . . . . . . . . 2-182.11 OPERATING ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-192.12 FLIGHT CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-192.13 KINDS OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-192.14 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-222.15 LIMITATION PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-242.16 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-28

2.16.1 FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-282.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-282.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-292.16.4 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . . 2-29

Operating Limitations DA 42 AFM


2.16.5 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . 2-292.16.6 GARMIN G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . 2-302.16.7 SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-342.16.8 GROUND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . 2-342.16.9 USE OF THE SUN VISORS . . . . . . . . . . . . . . . . . . . . . . . 2-34'



2.1 INTRODUCTION

Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markingsand placards necessary for the safe operation of the airplane, its powerplants, standardsystems and standard equipment.

The limitations included in this Chapter are approved.

WARNINGOperation of the airplane outside of the approved operatinglimitations is not permissible.



2.2 AIRSPEED

Airspeed IAS Remarks

vA Maneuveringspeed

above 1542 kg(3400 lb)

126 KIAS Do not make full or abruptcontrol surface movementabove this speed.

up to 1542 kg(3400 lb)

120 KIAS

vFE Max. flapsextended speed

LDG 111 KIAS Do not exceed these speedswith the given flap setting.

APP 137 KIAS

vLO Max. landinggear operatingspeed

Extension vLOE194 KIAS

Do not operate the landinggear above this speed.

Retraction vLOR156 KIAS

vLE Max. landing gear extended speed 194 KIAS Do not exceed this speedwith the landing gearextended.

vMCA Minimum control speed airborne 68 KIAS With one engine inoperativekeep airspeed above thislimit.

vNO Max. structural cruising speed 155 KIAS Do not exceed this speedexcept in smooth air, andthen only with caution.

vNE Never exceed speed in smooth air 194 KIAS Do not exceed this speedin any operation.



2.3 AIRSPEED INDICATOR MARKINGS

Marking KIAS Significance

White arc 56 - 111 KIAS Operating range with flaps fully extended.

Green arc 62 - 155 KIAS Normal operating range.

Yellow arc 155 - 194 KIAS Caution range - Only in smooth air.

Blue radial 82 KIAS Best rate of climb speed, single engine.

Red radial 68 KIAS Minimum control speed, single engine.

Red radial 194 KIAS Maximum speed for all operations - vNE.



2.4 POWER-PLANT LIMITATIONS

a) Number of engines : 2

b) Engine manufacturer : Thielert Aircraft Engines

c) Engine designation : TAE 125-01 Centurion 1.7

or'TAE 125-02-99 (if MM 42-198 is carried out)'(P/N see Equipment List in Chapter 6)

d) RPM limitations (shown as propeller RPM)Maximum : 2300 RPMMaximum overspeed : 2500 RPM (max. 20 sec)

e) Engine powerMax. take-off power : 99 kW (135 DIN-hp) at 2300 RPM (100 % load)Max. continuous power : 99 kW (135 DIN-hp) at 2300 RPM (100 % load)

f) Fuel temperature:''

' TAE 125-01' TAE 125-02-99'(MM 42-198 carried out)'

Minimum' -30 oC' -30 oC'

Maximum' +75 oC' +75 oC'

g) Oil pressure (indicated values are corrected for pressure altitude)Minimum : 1.0 barMaximum : 6.5 bar

h) Oil quantity (per engine)Minimum : 4.5 liters (appr. 4.8 US qts)Maximum : 6.0 liters (appr. 6.3 US qts)Maximum oil consumption : 0.1 liters/hr (appr. 0.1 US qts/hr)



i) Oil temperature:''




j) Gearbox temperatureMaximum : 120 C

k) Coolant temperature:''




l) Voltage

Minimum : 24.1 V

Maximum : 32.0 V

m) AmperageMaximum : 60 A

n) Propeller manufacturer : mt-Propeller

o) Propeller designation : MTV-6-A-C-F/CF 187-129

p) Propeller diameter : 187 cm (6 ft 2 in)

q) Prop. pitch angle (@ 0.75 R) : 12 0.2 (low pitch)

15 1 (start lock position)

81 1 (feathered position)



r) Approved fuel grades : see Section 2.14 - FUEL

s) Oil specification : SHELL HELIX ULTRA 5W30 synthetic API SL/CF

SHELL HELIX ULTRA 5W40 synthetic API SL/CF

AERO SHELL OIL Diesel 10W-40

t) Gearbox oil (propeller gearbox): SHELL EP 75W90 API GL-4

SHELL Spirax GSX 75W-80'

u) Coolant : Water / Cooler protection (BASF Glysantin ProtectPlus/G48) 1/1. The freezing point of the coolant is-36 C (-32.8 F).

CAUTIONIf the coolant or gearbox oil level is low, the reason must bedetermined and the problem must be corrected by authorizedpersonnel.

v) Maximum restart altitude : 6000 ft (TAE 125-01 engine installed)'

8000 ft (TAE 125-02-99 engine installed)'

w) Restart airspeed : 80 to 120 KIAS



2.5 ENGINE INSTRUMENT MARKINGS

Engine instrument markings and their color code significance are shown in the tablesbelow.

If the TAE 125-01 engine is installed:'

Indi-cation

Redarc/bar

=lower

prohibitedrange

Yellowarc/bar

=cautionrange

Greenarc/bar

=normal

operatingrange

Yellowarc/bar

=cautionrange

Redarc/bar

=upper

prohibitedrange

RPM -- -- up to2300 RPMabove

2300 RPM

Oilpressure

below1.0 bar 1.0 to 2.3 bar 2.3 to 5.2 bar 5.2 to 6.5 bar

above6.5 bar

Oiltemp.

below-32 C -32 to 50 C

50 to 125 C 150 to 130 C 2

125 to 140 C 1131 to 140 C 2

above140 C

Coolanttemp.

below-32 C -32 to 60 C

60 to 96 C 160 to 101 C 2

96 to 105 C 1102 to 105 C 2

above105 C

Gearboxtemp. -- -- up to 115 C 115 to 120 C

above120 C

Load -- -- 0 to 100 % -- --

Fueltemp.

below-30 C

-30 to -22 C 1-30 to +4 C 2

-22 to 70 C 1+5 to 69 C 2 70 to 75 C

above75 C

Ammeter -- -- up to 60 A -- above60 A

Volt-meter

below24.1 V 24.1 to 25 V 25 to 30 V 30 to 32 V

above32 V

Fuel qty. 0 US gal -- 0 to 25 US gal --

1) MM 42-101 not implemented2) MM 42-101 implemented (refer to Section 1.1)



If the TAE 125-02-99 engine is installed (MM 42-198 carried out):''

Indi-'cation'

Red'arc/bar'

='lower'

prohibited'range'

Yellow'arc/bar'

='caution'range'

Green'arc/bar'

='normal'

operating'range'

Yellow'arc/bar'

='caution'range'

Red'arc/bar'

='upper'

prohibited'range'

RPM' --' --' up to' 2300 RPM' --'above'

2300 RPM'

Oil'pressure'

below'1.0 bar' 1.0 to 2.3 bar' 2.3 to 5.8 bar' 5.8 to 6.5 bar'

above'6.5 bar'

Oil'temp.'

below'-30C' -30 to 50 C' 50 to 130 C' 131 to 140 C'

above'140 C'

Coolant'temp.'

below'-30 C' -30 to 60 C' 60 to 101 C' 102 to 105 C'

above'105 C'

Gearbox'temp.' --' --' up to 115 C' 115 to 120 C'

above'120 C'

Load' --' --' 0 to 100 %' --' --'

Fuel'temp.'

below'-30 C' -30 to +4 C' +5 to 69 C' 70 to 75 C'

above'75 C'

Ammeter' --' --' up to 60 A' --' above' 60 A'

Volt-'meter'

below'24.1 V' 24.1 to 25 V' 25 to 30 V' 30 to 32 V'

above'32 V'

Fuel qty.'' 0 US gal' --'

0 to 25 'US gal' --' --'



2.6 WARNING, CAUTION AND ADVISORY ALERTS

2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000

NOTEThe alerts described in the following are displayed on theGarmin G1000. Section 7.10 includes a detailed descriptionof the alerts.

The following tables show the color and significance of the warning, caution and advisoryalerts lights on the G1000.

Color and significance of the warning alerts on the G1000

Warning alerts(red) Meaning / Cause

WARNING One of the Warnings listed below is being indicated.

L/R ENG TEMP Left / Right engine coolant temperature is in the upper red range(too high/>105 C).

L/R OIL TEMP Left / Right engine oil temperature is in the upper red range (toohigh/>140 C).

L/R OIL PRES Left / Right engine oil pressure is in the lower red range (toolow/


Warning alerts(red) Meaning / Cause


L/R STARTER Left / Right engine starter is engaged.

DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closedand locked.

POSN ERROR G1000 will no longer provide GPS based navigational guidance.

ATTITUDE FAIL The display system is not receiving attitude reference informationfrom the AHRS.

AIRSPEED FAIL The display system is not receiving airspeed input from the airdata computer.

ALTITUDE FAIL The display system is not receiving altitude input from the air datacomputer.

VERT SPEEDFAIL

The display system is not receiving vertical speed input from theair data computer.

HDG The display system is not receiving valid heading input from theAHRS.

WARN RAIM position warning. The nav deviation bar is removed.



Color and significance of the caution alerts on the G1000

Caution alerts(amber) Meaning / Cause

L/R ECU A FAIL

* A fault has occurred in the left/right engine ECU A (one resetof minor faults is possible)

or* ECU A is being tested during FADEC-test procedure during

the 'before take-off check'.

L/R ECU B FAIL

* A fault has occurred in the left/right engine ECU B (one resetof minor faults is possible)

or* ECU B is being tested during FADEC-test procedure during

the 'before take-off check'.

L/R FUEL LOW Left / Right main tank fuel quantity is low.

L/R ALTN FAIL Left / Right engine alternator has failed.

L/R VOLTS LOW Left / Right engine bus voltage is too low (< 25 volts).

L/R COOL LVL Left / Right engine coolant level is low.

PITOT FAIL Pitot heat has failed.

PITOT HT OFF Pitot heat is OFF.

STAL HT FAIL Stall warning heat has failed.

STAL HT OFF Stall warning heat is OFF.

STICK LIMIT Control stick limiting system (variable elevator stop) has failed.

INTEG RAIM notavailable

RAIM (Receiver Autonomous Integrity Monitor) is not available.

AHRS ALIGN:Keep WingsLevel

The AHRS (Attitude and Heading Reference System) is aligning.

L/R AUX FUEL E Left / Right auxiliary fuel tank empty (if installed).

CHECK GEAR '(if installed)'

Landing gear is not down and locked.'



Color and significance of the advisory alerts on the G1000

Advisory alerts(white) Meaning / Cause

L/R GLOW ON Left/Right engine glow plug active.

L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress.

PFD FAN FAIL Cooling fan for the PFD is inoperative.

MFD FAN FAIL Cooling fan for the MFD is inoperative.

GIA FAN FAIL Cooling fan for the GIAs is inoperative.

2.6.2 OTHER WARNING ALERTS

Warning alerts on the instrument panel

GEAR UNSAFEWARNING LIGHT

(red)

Illuminates if the landing gear is neither in the final up nor in'the down & locked position.'

Audible warning alerts

GEARRETRACTEDCHIME TONE

(repeating)

Resounds if the landing gear is retracted while the flapsmove into position LDG or when the power lever is placed in'a position below 25%.



2.7 MASS (WEIGHT)

Value Mass (Weight)Minimum flight mass 1250 kg 2756 lbMaximum take-offmass

MM 42-088 not carried out 1700 kg 3748 lb'MM 42-088 carried out 1785 kg 3935 lb

Maximum zero fuel mass 1650 kg 3638 lbMaximum landing mass (see NOTE below) 1700 kg 3748 lbMax. load in nose baggage compartment(in fuselage nose)

30 kg 66 lb

Max. load in cabin baggage compartment(behind rear seats)

45 kg 100 lb

Max. load in baggage extension(behind cabin baggage compartment)

18 kg 40 lb

Max. load, cabin baggage compartment and baggageextension together

45 kg 100 lb

WARNINGExceeding the mass limits will lead to overstressing of theairplane as well as to degradation of flight characteristics andflight performance.

NOTEIn some countries the beginning of a flight is defined bystarting the powerplant. In those countries a ramp mass ofmaximal MTOM + 8 kg (MTOM + 18 lb) is approved. At thetime of lift-off the maximum permitted take-off mass must notbe exceeded.

NOTEIf MM 42-088 is carried out, a landing with a mass between1700 kg (3748 lb) and 1785 kg (3935 lb) is admissible. Itconstitutes an abnormal operating procedure. A "HardLanding Check" is only required after a hard landing,regardless of the actual landing mass.



2.8 CENTER OF GRAVITY

Datum Plane

The Datum Plane (DP) is a plane which is normal to the airplane*s longitudinal axis andin front of the airplane as seen from the direction of flight. The airplane*s longitudinal axisis parallel with the floor of the nose baggage compartment. When the floor of the nosebaggage compartment is aligned horizontally, the Datum Plane is vertical. The DatumPlane is located 2.196 meters (86.46 in) forward of the most forward point of the root ribon the stub wing (refer to figure in Section 6.2).

Center of gravity limitations

The center of gravity (CG position) for flight conditions must be between the followinglimits:

Most forward flight CG:

2.35 m (92.52 in) aft of Datum Plane at 1250 kg (2756 lb)2.35 m (92.52 in) aft of Datum Plane at 1468 kg (3236 lb)2.40 m (94.49 in) aft of Datum Plane at max. take-off mass (see Section 2.7)linear variation in between

Most rearward flight CG:

2.42 m (95.28 in) aft of Datum Plane at 1250 kg (2756 lb)2.49 m (98.03 in) aft of Datum Plane at 1600 kg (3527 lb)2.49 m (98.03 in) aft of Datum Plane at max. take-off mass (see Section 2.7)linear variation in between

Refer to Section 6.4.4 for a graphical illustration of the CG limitations.

WARNINGExceeding the center of gravity limitations reduces thecontrollability and stability of the airplane.



2.9 APPROVED MANEUVERS

The airplane is certified in the Normal Category in accordance with JAR-23.

Approved maneuvers

1) all normal flight maneuvers;

2) stalling (with the exception of dynamic stalling); and

3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in whichan angle of bank of not more than 60 is attained.

CAUTIONAerobatics, spinning and flight maneuvers with more than 60of bank are not permitted in the Normal Category. Stallingwith asymmetric power or one engine inoperative is notpermitted.



2.10 MANEUVERING LOAD FACTORS

NOTE'The tables below show structural limitations. The load factor'limits for the TAE 125 engine must also be observed. Refer'to the corresponding Operation & Maintenance Manual for'the engine.'

CAUTION'Avoid extended negative g-loads duration. Extended negative'g-loads can cause propeller control problems and engine'surging.'

at vA at vNE with flaps in APPor LDG position

Positive 3.8 3.8 2.0

Negative -1.52 0

WARNINGExceeding the maximum structural load factors will lead tooverstressing of the airplane.

CAUTIONExceeding the maximum powerplant load factors and timelimits listed below will lead to a L/R OIL PRES warning.

load factor time limit

-0.2 5 seconds

-0.3 4 seconds

-0.4 3 seconds

-0.5 2 seconds



2.11 OPERATING ALTITUDE

The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude.

2.12 FLIGHT CREW

Minimum crew : 1 (one person)

Maximum number of occupants : 4 (four persons)

2.13 KINDS OF OPERATION

Provided that national operational requirements are met, the following kinds of operationare approved:

daytime flights according to Visual Flight Rules (VFR) with the appropriate equipment: night flights according to Visual Flight Rules (VFR) with the appropriate equipment: flights according to Instrument Flight Rules (IFR) take-off and landing on paved surfaces take-off and landing on grass surfaces If OM 42-054 is carried out: flight into known or forecast icing conditions. Refer

to Supplement S03, latest revision.

Flights into known thunderstorms are prohibited.

Minimum operational equipment (serviceable)

The following table lists the minimum serviceable equipment required by JAR-23. Additionalminimum equipment for the intended operation may be required by national operatingrules and also depends on the route to be flown.

NOTEMany of the items of minimum equipment listed in thefollowing table are integrated in the G1000.



for daytime VFRflights

in additionfor night VFR flights

in additionfor IFR flights

Flight &naviga-tioninstru-ments

*

*

*

*

airspeed indicator(on G1000 PFD orbackup)

altimeter (on G1000PFD or backup)

magnetic compass

1 headset, used bypilot in command

*

*

*

*

*

*

*

*

vertical speedindicator (VSI)

attitude gyro(artificial horizon; onG1000 PFD orbackup)

turn & bank indicator(on G1000 PFD)

directional gyro

VHF radio (COM)with speaker andmicrophone

VOR receiver

transponder(XPDR), mode Aand mode C

GPS receiver (partof G1000)

*

*

*

*

*

*

second airspeedindicator (both, onG1000 PFD andbackup)

second altimeter(both, on G1000PFD and backup)

second attitude gyro(both, on G1000PFD and backup)

second VHF radio(COM)

VOR-LOC-GPreceiver

second GPSreceiver (part ofG1000)

engineinstru-ments

*

*

*

*

*

*

*

*

*

fuel qty. (2x)

oil press. (2x)

oil temp. (2x)

coolant temp. (2x)

coolant levelindicator (2x)

gearbox temp. (2x)

load (2x)

prop. RPM (2x)

fuel temp. left & righttank

*

*

ammeter

voltmeter


for daytime VFRflights

in additionfor night VFR flights

in additionfor IFR flights


lighting *

*

*

*

*

*

position lights

strobe lights (anticollision lights)

landing light

instrument lighting

flood light

flashlight

otheropera-tionalmini-mumequip-ment

*

*

*

*

*

stall warning system

variable elevatorstop

alternate means forfuel quantityindication (seeSection 7.9)

safety belts for eachoccupied seat

Airplane FlightManual

*

*

Pitot heating system

alternate static valve

* emergency battery(for backup attitudegyro and flood light)

NOTEA list of approved equipment can be found in Chapter 6.



2.14 FUEL

Approved fuel grades: JET A-1 (ASTM D 1655),'JET A (ASTM D 1655),'Jet Fuel No. 3 (GB6537-94),'and blends of the above listed Jet Fuel grades.'

Only if MM 42-037 is incorporated: Diesel (EN 590)'and blends of the above listed Jet Fuel grades'and Diesel.'

CAUTIONLimitations for DA 42 registered and/or operated in the'following countries:Indonesia, Malaysia: Use of Diesel Fuel is NOT approved.'

CAUTIONIf the airplane is operated with Diesel Fuel or a blend of DieselFuel with Jet Fuel, the use of the auxiliary tanks, if installed'(OM 42-056), is not permitted.

CAUTIONAdditional temperature limitations must be observed if theairplane is operated with Diesel Fuel or blends of Diesel Fuelwith Jet Fuel. Refer to Section 2.16.1.'

NOTEUse only uncontaminated fuel from reliable sources.



Main Tanks Auxiliary Tanks (if installed) Total

US gal liters US gal liters US gal litersTotal fuel quantity 2 x 26.0 2 x 98.4 2 x 13.7 2 x 52.0 2 x 39.7 2 x 150.4Usable fuel 2 x 25.0 2 x 94.6 2 x 13.2 2 x 50.0 2 x 38.2 2 x 144.6Max. permissibledifference LH/RH 5.0 18.9



EMERGENCY

Gear Extension

Max. 156 KIAS

LANDING GEARvLE / vLOE = 194 KIAS

vLOR = 156 KIAS

2.15 LIMITATION PLACARDS

All limitation placards are shown below. A list of all placards is included in the AirplaneMaintenance Manual (Doc. No. 7.02.01), Chapter 11.

On the instrument panel:

MM 42-088 or

OM 42-054 or

both

incorporated:

THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANEFLIGHT MANUAL IN THE NORMAL CATEGORY. PROVIDED THAT NATIONALOPERATIONAL REQUIREMENTS ARE MET AND THE APPROPRIATE EQUIPMENTIS INSTALLED AND OPERATIONAL, THIS AIRPLANE IS APPROVED FOR THEFOLLOWING KINDS OF OPERATION: DAY VFR, NIGHT VFR AND IFR, AND FLIGHTINTO KNOWN OR FORECAST ICING CONDITIONS. ALL AEROBATIC MANEUVERSINCLUDING SPINNING ARE PROHIBITED. FOR FURTHER OPERATIONAL LIMITATIONSREFER TO THE AIRPLANE FLIGHT MANUAL.

MANEUVERING SPEED:

VA = 126 KIAS (ABOVE 1542 KG / 3400 LB)VA = 120 KIAS (UP TO 1542 KG / 3400 LB)

neither

MM 42-088 nor

OM 42-054

incorporated:

THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANEFLIGHT MANUAL. IT CAN BE OPERATED IN THE NORMAL CATEGORY IN NON-ICINGCONDITIONS. PROVIDED THAT NATIONAL OPERATIONAL REQUIREMENTS ARE METAND THE APPROPRIATE EQUIPMENT IS INSTALLED, THIS AIRPLANE IS APPROVEDFOR THE FOLLOWING KIND OF OPERATION: DAY VFR, NIGHT VFR AND IFR. ALLAEROBATIC MANEUVERS INCLUDING SPINNING ARE PROHIBITED. FOR FURTHEROPERATIONAL LIMITATIONS REFER TO THE AIRPLANE FLIGHT MANUAL.

MANEUVERING SPEED:

VA = 124 KIAS (ABOVE 1468 UP TO 1700 KG / ABOVE 3236 UP TO 3748 LB)VA = 121 KIAS (1250 TO 1468 KG / 2756 TO 3236 LB)

On the Emergency Landing Gear Extension Lever:



Diesel Fuel orUnknown Fuel Blend:

Below -5 C:No engine start permitted.

Below +5 C:No take-off permitted.

max. usablefuel: 2 x 25 US galmax. difference LH/RH

tank: 5 US gal

max. usable fuel main tank:

2 x 25 US galauxiliary tank:2 x 13 US gal

max. difference LH/RHmain tank: 5 US gal

WARNINGAPPROVED FUEL

JET-A1or see Airplane Flight Manual

On the instrument panel, next to the fuel quantity indication:

(a) Standard Tank: (b) Auxiliary Tank (if installed):

if MM 42-037 is carried out, on the Garmin G1000 MFD next to the fuel temperature

indication:

(a) Next to each of the two fuel filler necks;

(b) in addition next to each of the two auxiliary fuel filler necks (if installed):



OILShell Helix Ultra

5W30 synth.

API SL/CF

or see AFM

UP

Flaps

APP137 KIAS

LDG 111 KIAS

In each cowling, on the door for the oil filler neck:

Next to the flap selector switch:

In the cabin, on the left fuselage sidewall:'



Next to the cabin baggage compartment:'

'

'

'

'

'

'

'

'

'

In the nose baggage compartment:

Beside the door locking device installed in the passengers* door:

On the right-hand side of the instrument panel above the circuit breakers:

Max. Baggage:

30 kg [66 lb]

EMERGENCY EXIT:The keylock must beunlocked during flight

______ NO SMOKING ______



2.16 OTHER LIMITATIONS

2.16.1 FUEL TEMPERATURE

JET A-1, JET A and Jet Fuel No. 3:'from -30 C to +75 C (from -22 F to +167 F)'

NOTEOperation with Diesel Fuel, or blends of Diesel Fuel with JetFuel, is only approved when MM 42-037 is incorporated.

Diesel Fuel, Blends of Diesel Fuel with Jet Fuel, or unknown fuel grade:'Engine starting fuel temperature . . . . . . . . . min. -5 C (+23 F)'Take-off fuel temperature . . . . . . . . . . . . . . . min. +5 C (+41 F)'Maximum fuel temperature . . . . . . . . . . . . . +75 C (+167 F)'

2.16.2 BATTERY CHARGE

Taking off for a Night VFR or IFR flight with an empty battery is not permitted.

The use of an external power supply for engine starting with an empty airplane batteryis also not permitted if the subsequent flight is intended to be a Night VFR or IFR flight.In this case the airplane battery must first be charged.



2.16.3 EMERGENCY SWITCH

IFR flights are not permitted when the seal on the emergency switch is broken.

2.16.4 DOOR LOCKING DEVICE

The canopy and the passenger door must not be blocked by the key lock during operationof the airplane.

2.16.5 ELECTRONIC EQUIPMENT

The use and switching on of electronic equipment other than that which is part of theequipment of the airplane is not permitted, as it could lead to interference with theairplane*s avionics.

Examples of undesirable items of equipment are:

- Mobile phones- Remote radio controls- Video screens employing CRTs- Minidisc recorders in record mode

This list is not exhaustive.

The use of laptop computers, including those with CD-ROM drives, CD and minidiscplayers in the replay mode, cassette players and video cameras is permitted. All thisequipment however should be switched off for take-off and landing.



2.16.6 GARMIN G1000 AVIONICS SYSTEM

1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00406-00, dated September2004 or later appropriate revision must be immediately available to the flight crew.

2. If MM-42-101 has been implemented (refer to Section 1.1), the G1000 must utilizethe software Garmin P/N: 010-00370-11, or later approved software in accordancewith the mandatory service bulletin DAI MSB 42-008, latest version.

3. If MM 42-198 (TAE 125-02-99 engines, refer to Section 1.1) is implemented, theG1000 must utilize the software Garmin P/N 010-00370-15, or later approved softwarein accordance with the mandatory service bulletin DAI MSB42-008, latest version.

Software Part Number ApprovedVersion

Function

System

for a

ppro

ved

vers

ion

see

DA

I MS

B 4

2-00

8, la

test

ve

rsio

n

010-00370-( )Manifest006-B0093-( ) GPS1, GPS2006-B0172-( ) GTX1-GIA1, GTX1-GIA2006-B0190-( ) GIA1, GIA2006-B0193-( ) GEA1-GIA1; GEA1-GIA2006-B0203-( ) GMA1-GIA1, GMA1-GAI2006-B0223-( ) GRS1-GIA1, GRS1-GIA2006-B0224-( ) GMU1006-B0319-( ) PFD1, MFD1006-B0328-( )006-B0329-( )006-C0048-( ) GMU1 FPGA006-C0049-( ) GRS1 FPGA006-C0055-( ) GDC1 FPGA006-D0159-( ) GRS1 MV DB


Software Part Number ApprovedVersion

Function


006-D0202-( ) for approvedversion see

DAI MSB 42-

008, latest

version

006-B0261-( ) GDC1-GIA1006-B0081-( ) COM1, COM2006-B0083-( ) GS1, GS2006-B0082-( ) NAV1, NAV2

NOTEThe database version is displayed on the MFD power-up pageimmediately after system power-up and must beacknowledged. The remaining system software versions canbe verified on the AUX group sub-page 5, "AUX-SYSTEMSTATUS".

4. IFR enroute, oceanic and terminal navigation predicated upon the G1000 GPS Receiveris prohibited unless the pilot verifies the currency of the database or verifies eachselected way point for accuracy by reference to current approved data.

5. Instrument approach navigation predicated upon the G1000 GPS Receiver must beaccomplished in accordance with approved instrument approach procedures that areretrieved from the GPS equipment database. The GPS equipment database mustincorporate the current update cycle.

NOTENot all published approaches are in the FMS database. Thepilot must ensure that the planned approach is in thedatabase.



(a) Instrument approaches utilizing the GPS receiver must be conducted in theapproach mode and Receiver Autonomous Integrity Monitoring (RAIM) mustbe available at the Final Approach Fix.

(b) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type ofapproach not approved for GPS overlay with the G1000 GPS receiver is notauthorized.

(c) Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPSrequire VOR/ILS navigation data to be present on the display.

(d) When an alternate airport is required by the applicable operating rules, it mustbe served by an approach based on other than GPS or Loran-C navigation,the airplane must have the operational equipment capable of using thatnavigation aid, and the required navigation aid must be operational.

(e) VNAV information may be utilized for advisory information only. Use of VNAVinformation for Instrument Approach Procedures does not guarantee step-downfix altitude protection, or arrival at approach minimums in normal position to land.

(f) RNAV (GPS) approaches must be conducted utilizing the GPS sensor.

(g) RNP RNAV operations are not authorized, except as noted in Chapter 1 of thisAFM.

6. If not previously defined, the following default settings must be made in the "SYSTEMSETUP" menu of the G1000 prior to operation (refer to Pilot*s Guide for procedureif necessary):

(a) DIS, SPD : nm, kt (sets navigation units to "nautical miles" and "knots")

(b) ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute")

(c) MAP DATUM : WGS 84 (sets map datum to WGS-84, see note below)

(d) POSITION : deg-min (sets navigation grid units to decimal minutes)



NOTEIn some areas, datums other than WGS-84 or NAD-83 maybe used. If the G1000 is authorized for use by the appropriateAirworthiness Authority, the required geodetic datum mustbe set in the G1000 prior to its use for navigation.

7. When AHRS is required to meet the items listed in the Minimum operational equipment'(serviceable) table in Section 2.13 of this AFM, operation is prohibited in the following'areas:'

(a) north of 70 N and south of 70 S latitudes,'

(b) north of 65 N between 75 W and 120 W longitude, and'

(c) south of 55 S between 120 E and 165 E longitude.'

When day VFR operations are conducted in the above areas, the MFD must be in'a non-Heading Up orientation.'

8. CDI sequencing of the ILS must be set to MANUAL for instrument approachesconducted with the autopilot coupled. If the CDI source is changed when the autopilotis engaged in NAV mode, the autopilot lateral mode will revert to ROLL ATTITUDEmode and NAV mode must be manually reselected by the pilot.

9. The fuel quantity, fuel required, and fuel remaining functions on the Fuel Page(displayed when pushing the FUEL button as shown in Section 7.13) of the FMS aresupplemental information only and must be verified by the flight crew.

10. The pilot*s altimeter is the primary altitude reference during all operations usingadvisory vertical navigation (VNAV) information and the autopilot. A flight altitude'selected via the autopilot must be verified and corrected according to the indication'of the calibrated altimeter.'



2.16.7 SMOKING

Smoking in the airplane is not permitted.

2.16.8 GROUND OPERATION

Take-off and landing has been demonstrated on hard paved surfaces (asphalt, concrete,etc.) and grass runways.

2.16.9 USE OF THE SUN VISORS'

The sun visors (if installed, OM 42-101) may only be used during cruise. During all other'phases of flight the sun visors must be locked in the fully upward position.'

DA 42 AFMEmergencyProcedures


CHAPTER 3EMERGENCY PROCEDURES

Page

3.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-43.1.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-43.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES . . . . . . . . . . . . . . 3-53.1.3 SELECTING EMERGENCY FREQUENCY . . . . . . . . . . . . . . 3-5

3.2 AIRPLANE-RELATED G1000 WARNINGS . . . . . . . . . . . . . . . . . . . 3-63.2.1 WARNINGS / GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-63.2.2 L/R ENG TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-63.2.3 L/R OIL TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-83.2.4 L/R OIL PRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-93.2.5 L/R GBOX TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-103.2.6 L/R FUEL TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-113.2.7 L/R ALTN AMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-123.2.8 L/R ENG FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-123.2.9 L/R STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-133.2.10 DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13

3.3 G1000 SYSTEM WARNINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-143.3.1 RED X . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-143.3.2 POSN ERROR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-143.3.3 ATTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-143.3.4 AIRSPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-143.3.5 ALTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-153.3.6 VERT SPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-153.3.7 HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-153.3.8 WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15

EmergencyProcedures

DA 42 AFM


3.4 G1000 FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-163.4.1 NAVIGATION INFORMATION FAILURE . . . . . . . . . . . . . . 3-163.4.2 PFD OR MFD DISPLAY FAILURE . . . . . . . . . . . . . . . . . . . 3-163.4.3 AHRS FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-173.4.4 AIR DATA COMPUTER (ADC) FAILURE . . . . . . . . . . . . . . 3-173.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-183.4.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-193.5 ONE ENGINE INOPERATIVE PROCEDURES . . . . . . . . . . . . . . . 3-20

3.5.1 DETECTING THE INOPERATIVE ENGINE . . . . . . . . . . . . 3-203.5.2 ENGINE TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . 3-213.5.3 ENGINE SECURING (FEATHERING) PROCEDURE . . . . 3-243.5.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-253.5.5 ENGINE FAILURE DURING TAKE-OFF . . . . . . . . . . . . . . . 3-293.5.6 ENGINE FAILURES IN FLIGHT . . . . . . . . . . . . . . . . . . . . . 3-323.5.7 LANDING WITH ONE ENGINE INOPERATIVE . . . . . . . . . 3-353.5.8 GO-AROUND / BALKED LANDING WITH ONE ENGINE

INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-383.5.9 FLIGHT WITH ONE ENGINE INOPERATIVE . . . . . . . . . . . 3-40

3.6 LANDING GEAR SYSTEM FAILURES . . . . . . . . . . . . . . . . . . . . . 3-413.6.1 LANDING GEAR UNSAFE WARNING . . . . . . . . . . . . . . . . 3-413.6.2 MANUAL EXTENSION OF THE LANDING GEAR . . . . . . . 3-433.6.3 LANDING WITH GEAR UP . . . . . . . . . . . . . . . . . . . . . . . . . 3-453.6.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING

GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-463.6.5 LANDING WITH DEFECTIVE BRAKES . . . . . . . . . . . . . . . 3-47

3.7 FAILURES IN THE ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . 3-483.7.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-483.7.2 HIGH CURRENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-49



3.7.3 STARTER MALFUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3-493.8 SMOKE AND FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-50

3.8.1 ENGINE FIRE ON GROUND . . . . . . . . . . . . . . . . . . . . . . . . 3-503.8.2 ENGINE FIRE DURING TAKE-OFF . . . . . . . . . . . . . . . . . . . 3-503.8.3 ENGINE FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-513.8.4 ELECTRICAL FIRE ON GROUND . . . . . . . . . . . . . . . . . . . . 3-523.8.5 ELECTRICAL FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . 3-53

3.9 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-543.9.1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE

CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-543.9.2 UNLOCKED DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-553.9.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM . . 3-563.9.4 UNINTENTIONAL FLIGHT INTO ICING . . . . . . . . . . . . . . . . 3-583.9.5 FUEL SUPPLY FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-593.9.6 RECOVERY FROM AN UNINTENTIONAL SPIN . . . . . . . . . 3-603.9.7 EMERGENCY DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-623.9.8 EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-62

NOTEProcedures for uncritical system faults are given in Chapter4B - ABNORMAL OPERATING PROCEDURES.

EmergencyProcedures

DA 42 AFM


3.1 INTRODUCTION

3.1.1 GENERAL

This chapter contains checklists as well as the description of recommended proceduresto be followed in the event of an emergency. Engine failure or other airplane-relatedemergencies are most unlikely to occur if the prescribed procedures for pre-flight checksand airplane maintenance are followed.

If, nonetheless, an emergency does arise, the guidelines given in this chapter should befollowed and applied in order to clear the problem.

As it is impossible to foresee all kinds of emergencies and cover them in this AirplaneFlight Manual, a thorough understanding of the airplane by the pilot is, in addition to hisknowledge and experience, an essential factor in the solution of any problems which mayarise.

WARNINGIn each emergency, control over the flight attitude and thepreparation of a possible emergency landing have priorityover attempts to solve the current problem ("first fly theaircraft"). Prior to the flight the pilot must consider thesuitability of the terrain for an emergency landing for eachphase of the flight. For a safe flight the pilot must constantlykeep a safe minimum flight altitude. Solutions for variousadverse scenarios should be thought over in advance. Thisshould prevent a situation where the pilot is faced with anemergency he cannot handle calmly and with determination.



3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES

Event Airspeed

One engine inoperative minimumcontrol speed (Air) vmCA

68 KIAS

One engine inoperative speed forbest rate of climb vYSE

82 KIAS

3.1.3 SELECTING EMERGENCY FREQUENCY

In an in-flight emergency, depressing and holding the Com transfer button on theG1000 for 2 seconds will tune the emergency frequency of 121.500 MHz. If the displayis available, it will also show it in the "Active" frequency window.

EmergencyProcedures

DA 42 AFM


3.2 AIRPLANE-RELATED G1000 WARNINGS

3.2.1 WARNINGS / GENERAL

"Warning" means that the non-observation of the corresponding procedure leads to animmediate or important degradation in flight safety. The warning text is displayed in redcolor. A warning chime tone of 1.5 seconds duration will sound and repeat without delayuntil the alarm is acknowledged by the crew.

3.2.2 L/R ENG TEMP

L/R ENG TEMP Left / Right engine coolant temperature is in the upperred range (too high / above 105 C)

Coolant temperatures above the limit value of 105 C can lead to a total loss of powerdue to engine failure.

- Check G1000 for L/R COOL LVL caution message (low coolant level).

L/R COOL LVL caution message not displayed:

during climb:

- Reduce power on affected engine by 10 % or more as required.- Increase airspeed by 10 KIAS or more as required.- If the coolant temperature does not reach the green range within 60 seconds,

reduce power on affected engine as far as possible and increase airspeed.

CONTINUED



during cruise:

- Reduce power on affected engine.- Increase airspeed.- Check coolant temperature in green range.

CAUTIONIf high coolant temperature is indicated and the L/R COOLLVL caution message is not displayed, it can be assumed thatthere is no technical defect in the cooling system and that theabove mentioned procedure can decrease the temperature(s).This might not be the case if the coolant temperature doesnot return to the green range. In this case perform aprecautionary landing on the nearest suitable airfield. Preparefor an engine failure in accordance with 3.5.6 - ENGINEFAILURES IN FLIGHT.

L/R COOL LVL caution message displayed:

- Reduce power on affected engine.- Expect loss of coolant.

WARNINGA further increase in coolant temperature must be expected.Prepare for an engine failure in accordance with3.5.6 - ENGINE FAILURES IN FLIGHT.

END OF CHECKLIST

EmergencyProcedures

DA 42 AFM


3.2.3 L/R OIL TEMP

L/R OIL TEMP Left / Right engine oil temperature is in the upper redrange (too high / above 140 C).

Oil temperatures above the limit value of 140 C can lead to a total loss of power dueto engine failure.

- Check oil pressure.If the oil pressure is outside of the green range (lower limit):

- Reduce power on affected engine.- Expect loss of engine oil.

WARNINGA further increase in oil temperature must be expected.Prepare for an engine failure in accordance with3.5.6 - ENGINE FAILURES IN FLIGHT.

if the oil pressure is within the green range:

- Reduce power on affected engine.- Increase airspeed.

CAUTIONIf high oil temperature is announced and the oil pressureindication is within the green range, it can be assumed thatthere is no technical defect in the engine oil system and thatthe above mentioned procedure can decrease thetemperature(s). This might not be the case if the oiltemperature does not return to the green range. In this caseperform a precautionary landing on the nearest suitableairfield. Prepare for an engine failure in accordance with 3.5.6 - ENGINE FAILURES IN FLIGHT.

END OF CHECKLIST



3.2.4 L/R OIL PRES

L/R OIL PRES Left / Right engine oil pressure is in the lower redrange (too low / below 1 bar).

Oil pressures below the limit value of 1 bar can lead to a total loss of power due to enginefailure.

- Reduce power on affected engine.- Expect loss of oil.

WARNINGLand at the nearest suitable airfield. Prepare for an enginefailure in accordance with 3.5.6 - ENGINE FAILURES INFLIGHT.

END OF CHECKLIST

EmergencyProcedures

DA 42 AFM


3.2.5 L/R GBOX TEMP

L/R GBOX TEMP Left / Right engine gearbox temperature is in the upperred range (too high / above 120 C).

Gearbox temperatures above the limit value of 120 C can lead to a total loss of powerdue to engine failure.


CAUTIONAt high ambient temperature conditions and/or at lowairspeeds with high power settings, it can be assumed thatthere is no technical defect in the gearbox and that the abovementioned procedure will decrease the temperature(s). Thismight not be the case if the gearbox temperature does notreturn to the green range. In this case perform a precaution-ary landing on the nearest suitable airfield. Prepare for anengine failure in accordance with 3.5.6 - ENGINE FAILURESIN FLIGHT.

END OF CHECKLIST



3.2.6 L/R FUEL TEMP

L/R FUEL TEMP Left / Right fuel temperature is in the upper red range (toohigh / above 75 C).

Fuel temperatures above the limit value of 75 C can lead to a noticeable reduction ofthe high pressure pump efficiency.


CAUTIONAt high ambient temperature conditions and/or at lowairspeeds with high power settings and low fuel quantities,it can be assumed that the above mentioned procedure willdecrease the temperature(s). If the fuel temperature does notreturn to the green range, perform a precautionary landingon the nearest suitable airfield.

NOTEIncreased fuel temperature can occur when the fuel quantityin the main tank is low. If the auxiliary tank is installed the fueltemperature can be decreased by transferring fuel from theauxiliary to the main tank.

END OF CHECKLIST

EmergencyProcedures

DA 42 AFM


3.2.7 L/R ALTN AMPS

L/R ALTN AMPS Left / Right engine alternator output is in the upper redrange (too high / above 60 amps).

Proceed according to:

3.7.2 - HIGH CURRENT

3.2.8 L/R ENG FIRE

L/R ENG FIRE Left / Right engine fire detected

Engine fire can lead to a total loss of power due to engine failure as well as severestructural damage:

Proceed according to the following procedures as applicable:

3.8.1 - ENGINE FIRE ON GROUND

3.8.2 - ENGINE FIRE DURING TAKE-OFF

3.8.3 - ENGINE FIRE IN FLIGHT



3.2.9 L/R STARTER

L/R STARTER Left / Right engine starter is engaged


3.7.3 - STARTER MALFUNCTION

3.2.10 DOOR OPEN

DOOR OPEN Front and/or rear canopy and/or baggage door are/is notclosed and locked.


3.9.2 - UNLOCKED DOORS

EmergencyProcedures

DA 42 AFM


3.3 G1000 SYSTEM WARNINGS

3.3.1 RED X

A red X through any display field, such as COM frequencies, NAV frequencies, or enginedata, indicates that display field is not receiving valid data.

3.3.2 POSN ERROR

POSN ERROR The system will flag and no longer provide GPS basednavigational guidance.

Revert to the G1000 VOR/ILS receivers or an alternate means of navigation other thanthe G1000 GPS receivers.

3.3.3 ATTITUDE FAIL

ATTITUDE FAIL The display system is not receiving attitude referenceinformation from the AHRS; accompanied by the removalof sky/ground presentation and a red X over the attitudearea.

Revert to the standby attitude indicator.

3.3.4 AIRSPEED FAIL

AIRSPEED FAIL The display system is not receiving airspeed input fromthe air data computer; accompanied by a red X throughthe airspeed display.

Revert to the standby airspeed indicator.



3.3.5 ALTITUDE FAIL

ALTITUDE FAIL The display system is not receiving altitude input from theair data computer; accompanied by a red X through thealtimeter display.

Revert to the standby altimeter.

3.3.6 VERT SPEED FAIL

VERT SPEED FAIL The display system is not receiving vertical speed inputfrom the air data computer; accompanied by a red Xthrough the vertical speed display.

Determine vertical speed based on the change of altitude information.

3.3.7 HDG

HDG The display system is not receiving valid heading inputfrom the AHRS; accompanied by a red X through thedigital heading display.

Revert to the emergency compass.

3.3.8 WARN

WARN RAIM position warning - nav deviation bar removed.

1. CDI softkey . . . . . . . . . . . . . . . . . . . . . . . . . . switch to VOR/LOC

EmergencyProcedures

DA 42 AFM


3.4 G1000 FAILURES

3.4.1 NAVIGATION INFORMATION FAILURE

If Garmin G1000 GPS navigation information is not available or invalid, utilize remainingoperational navigation equipment as required.

3.4.2 PFD OR MFD DISPLAY FAILURE

1. DISPLAY BACKUP button on audio panel . . PUSH

Automatic Entry of Display Failure'

- If the PFD and MFD have automatically entered reversionary mode, use the following'procedure.'

(a) DISPLAY BACKUP button on audio panel . . PUSH (button will be OUT)'

NOTE'After automatic entry of reversionary mode, the pilot must'press the DISPLAY BACKUP button on the audio panel. After'the DISPLAY BACKUP button has been pushed, the system'will remain in reversionary mode even if the problem causing'the automatic entry of reversionary mode is resolved. A'maximum of one attempt to return to normal mode is'approved using the following procedure.'

(b) DISPLAY BACKUP button on audio panel . . PUSH (button will be IN)'

- If the system returns to nor

Diamond DA42 Twin Star Aircraft Flight Manual

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